setting reference values to find Cd, Cl, Cm (3D)
 

Hi !

I'm trying to simulate a small experimental rocket (1,5m tall) in order t oget its aerodynamic coeff (Cd, Cl, and Cm at low angle of attack : 1°).

The problem is that I have a Cd=2500 !!

I think that may come from the ref. values...

Here is my mesh : http://img145.imageshack.us/img145/9...illage15dv.png

What sould I fill in area ? The cross area, or total area ? And for lenght... ?

I've computed from my environment (a half cylinder, in pressure far filed).

Any help is welcome !!

Thank you !!